Abstract: A vehicle control method of starting and shutting down an engine, in which a processor receives a blockchain update comprising a first transaction with instructions to perform an engine startup or shutdown; the blockchain update is validated; an engine startup or shutdown is performed based on the validated blockchain update; where the engine startup or shutdown is delayed based on validating a predetermined number of subsequent blockchain updates, including a second transaction with instructions to perform the engine startup or shutdown.

Abstract: A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.

Abstract: An assembly in a turbine engine having a dynamically moveable flowpath boundary member for encasing a rotatable bladed disc and maintaining a clearance gap between the flowpath boundary member and the blade tips of the bladed disc. The assembly comprises a static casing, a flowpath boundary member carried by the casing, and a refrigeration system configured to remove heat from the flowpath boundary member to thereby thermally expand and contract the flowpath boundary member to control blade tip clearance.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver is coupled to a closed form refrigeration system having an evaporator, a compressor, a condenser, an expansion valve, and a refrigerant contained therein. The thermal driver is cooled by the refrigeration system, and the rate of cooling causes expansion and contraction of the thermal driver that is translated by linkages into axially forward and aft motion of the shroud.

Abstract: A method for controlling an engine having a control module and smart nodes. The method includes maintaining a block chain ledger, which includes an information block from at least a preceding engine start, may be at the control module of the aircraft engine. The method also includes maintaining a hash of at least a digital certificate and data at one of the smart nodes; transmitting a message including the hash to the control module; receiving the message at the control module; determining a control hash based upon the information from at least a preceding engine start at the control module; module comparing the hash to the control hash at the control; and based upon the comparison, starting the engine and updating the block chain ledger as a function of the received message.

Abstract: A vehicle control method of starting and shutting down an engine, in which a processor receives a blockchain update comprising a first transaction with instructions to perform an engine startup or shutdown; the blockchain update is validated; an engine startup or shutdown is performed based on the validated blockchain update; where the engine startup or shutdown is delayed based on validating a predetermined number of subsequent blockchain updates, including a second transaction with instructions to perform the engine startup or shutdown.

Abstract: A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.

Abstract: A gas turbine engine includes a turbine and a rotor tip clearance control system. The rotor tip clearance control system is configured to actively manage a clearance formed between a rotor of the turbine and a case structure of the turbine.

Abstract: According to one aspect, an apparatus for controlling a vane comprises an actuator, a vane control rod, a guide pin disposed on the vane control rod, a sleeve disposed about the vane control rod, and at least one sleeve track disposed along an extent of the sleeve. Further in accordance with this aspect, the guide pin couples the vane control rod and the sleeve, and the actuator linearly moves the vane control rod through the sleeve in order to manipulate a position of the vane.

Abstract: A turbine engine includes a fan connected to a fan shaft, a combustion chamber, and an electric motor/generator in communication with the fan shaft. A controller is configured to direct power into the electric motor/generator during engine accelerations from steady state such that air flow to the combustion chamber is increased. The controller is further configured to direct power out of the electric motor/generator during engine decelerations from steady state such that air flow to the combustion chamber is decreased.

Abstract: Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

Abstract: An assembly in a turbine engine having a dynamically moveable flowpath boundary member for encasing a rotatable bladed disc and maintaining a clearance gap between the flowpath boundary member and the blade tips of the bladed disc. The assembly comprises a static casing, a flowpath boundary member carried by the casing, and a refrigeration system configured to remove heat from the flowpath boundary member to thereby thermally expand and contract the flowpath boundary member to control blade tip clearance.

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver is coupled to a closed form refrigeration system having an evaporator, a compressor, a condenser, an expansion valve, and a refrigerant contained therein. The thermal driver is cooled by the refrigeration system, and the rate of cooling causes expansion and contraction of the thermal driver that is translated by linkages into axially forward and aft motion of the shroud.

Abstract: A gas turbine engine includes a turbine and a rotor tip clearance control system. The rotor tip clearance control system is configured to actively manage a clearance formed between a rotor of the turbine and a case structure of the turbine.

Abstract: According to one aspect, an apparatus for controlling a vane comprises an actuator, a vane control rod, a guide pin disposed on the vane control rod, a sleeve disposed about the vane control rod, and at least one sleeve track disposed along an extent of the sleeve. Further in accordance with this aspect, the guide pin couples the vane control rod and the sleeve, and the actuator linearly moves the vane control rod through the sleeve in order to manipulate a position of the vane.

Abstract: A propulsion system includes a gas turbine engine, an inlet particle separator, an infrared suppression system, and an engine controller. The engine controller may be configured to determine an activation state of the inlet particle separator, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on inlet flow, which is determined based on the activation state. The engine controller may be further configured to determine an activation state of the infrared suppression system, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on backpressure, which is determined based on the activation state.

Abstract: Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

Abstract: A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine. The controller system is configured to identify a set point reference of the first component, identify a set point reference of the second component, and identify a data set indicative of a level of deterioration of the gas turbine engine. The controller system is also configured to change the set point reference of the first component to extend a lifespan of the gas turbine engine and/or change the set point reference of the second component to extend the lifespan of the gas turbine engine.

Abstract: A system for controlling operation of an aircraft engine includes a master controller, a control node coupled to a component of the aircraft engine and to the master controller, wherein the control node includes a computing device for performing diagnosis of the component. The computing device is configured to assess performance of the component during operation of the aircraft, determine whether the component is performing within specification, and if not performing within specification, indicate that the component is out of specification.

Abstract: A real-time engine management system having a controller system configured to control demand on a first component of an engine. The controller system is also configured to access a first set of prognostic data about the first component, where the first set of prognostic data includes a remaining lifespan approximation of the first component operating at a present operating condition. The controller system is also configured to identify a temporal length of an engine procedure operating at the present operating condition, alter a current limit constant associated with the first component to increase the remaining lifespan approximation of the first component beyond the temporal length, and implement the current limit constant associated with the first component so that the first component does not fault during the engine procedure.